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Патент USA US3096052

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July 2, 1963
Filed Oct. 1, 1954
United States Patent O
Patented July 2, 1963
make predeterminedly controlled steering possible; and
with the latter to facilitate even substantially vertical
ascent and ‘descent of the vehicle.
Fernando G. Prieto, Los Angeles, Calif.
(3a. Calle Poniente 904, San Salvador, El Salvador)
Filed Get. 1, 1954, Ser. No. 459,625
2 Claims. (Cl. 244-12)
When engine 6 is operating and its longitudinal axis 3
is not parallel to the longitudinal axis 15 of the vehicle,
Athe latter will turn around a vertical line through its cen
ter, and said rotation will last until parallelism isV effected
between said axes.
The means 7 `in FIGS. `l and 2 inclu-des a circular and
The present invention relates to improvements in llying
vehicles and is a continuation-in-part of my pending ap
plication Serial No. 410,@61, filed Feb. l5, 1054, now 10 horizontal trackway 10 «fixedly mounted on the vehicle as
a reinforcement for adjacent top and side wall areas; and
also includes a circular member 11 tracking in said track
The wings of a conventional airplane, when the vehicle
way yand »adapted to revolve in a horizontal plane. Said
moves through the lair, are constantly inclined to the for
trackway and said member are so interconnected, at 12,
-ward line of flight in order to create a lifting force and
overcome the pull of gravity. Said inclination, called the 15 as to retain member 11 against vertical displacement from
said trackway, yand yet enable free rotational adjustment
angle of attack, also produces a drag which reduces the
of member 11 by any suitable control means. Trackway
speed of the vehicle and lessens its efficiency.
10 takes the form of a depending circular top and side
One object of the invention is to provide a combina
Wall area reinforcing ilange whose lower edge terminates
tion of a vehicle and at least two reaction engines having
independent and different action. The purpose of one 20 4at yapproximately the plane of the uppermost portion of
the rear fuselage opening so as not `to interfere with en
or more engines is to vertically lift the vehicle while the
gine 6 discharge. FIG. 2 shows the rear fuselage open
purpose of the other one or more engines is to propel said
ing as being of much greater widthwise area than the
vehicle in any desired direction transverse to the lift.
discharge end of engine 6.
That is, the vehicle is provided with engines having dif
As shown, the engine 6 is placed Within the vehicle 5
ferent purposes but both engines always cooperating to 25
and -atllxed to member 11 as by suitable connection 13.
propel the vehicle with a minimum `drag and a maximum
Said engine 6 land means 7 may be disposed at any posi
tion where the thrust of the engine is effective to propel .
Another object of the invention is to provide the ve
the vehicle forward.
hicle of said combination with ability to quickly maneu
The forms :of the invention that are illustrated are sub
ver and/or change direction.
stantially similar, except for arrangement. =ln FIG. 3,
A further object of the invention is to obviate the need
the engine 6 and member 11 are inverted from the show
for complex apparatus such as wings and propellers which
ing in FIG. l.
impede or prevent conventional vehicles attaining super
sonic speeds.
The foregoing and other objects, features, and advan
The means 7 also comprises an operating member such
35 as cable 16 that may be controlled by a steering wheel.
Said cable may be guided as by pulleys 17 and trained
tages of the invention will become more cle-arly evident
from the following detailed description of an exemplary
form of invention, the same being illustrated in the ac
companying drawing, in which:
FIG. l is a side elevational View, partly in section, of
either around member 11 or over a pulley afiixed to said
The dot-dash line positions of engine 6 (FIG. 2) indi
cate examples of the multiplicity of positions the engine
can take to direct the movement of the vehicle. ln this
one form of vehicle and propulsion means according to
respect, the showing in FIGS. l and 2 lare similar.
the invention.
The means 7a is represented by flange 14 which atñxes
FIG. 2 is -a top plan view, partly broken away, and
the engine 6a preferably inside the vehicle at its lower ‘
shown in section.
45 wall. Said engine or engines are placed in a position with
FIG. 3 is a fragmentary sectional View of another form
the axis 8a vertical, the head upward, and the mouth pref
of the invention, the same showing a modified form of
erably flush with said lower wall.
vehicle propelling means.
When vehicle 5, once in the air, has attained a desired
ln the drawing, FIGS. 1 and 2 show in combination a
height, the engine or engines 6a may reduce its opera
wingless vehicle ‘S having reaction engines 6 and 6a and
tional speed just suñlcient to overcome the pull of gravity.
means 7 and 7a mounting said engines. The engines 6,
6a discharge through rear and bottom fuselage-provided
wall openings, as shown.
The engines 6 and 6a are of vany type of reaction en
gine that creates thrust `along its axis 8 or Sa, as the case
may be. Examples of such engines `are jet motors and
the engine ‘disclosed in my Patent No. 2,481,672.
The vehicle shown is generally elliptical in plan has a
The engine or engines 6 may then start operating at the
desired flight speed of the vehicle. lt is evident there
fore, that the combined operation of both engines 6 and
6a may adjustably move the vehicle 5 universally, so as
to propel the same in any desired direction.
substantially plane bottom wall and merging top and side
Since the position of the vehicle, due to the present
combination, is always horizontal, it is evident that its
drag is reduced to a minimum and its elllciency main
walls which are convexly curved both transversely and
tained to a maximum.
It is also evident that the vehicle may be ground
longitudinally `throughout the length and breadth of the 60
borne or water-borne as well as air-borne.
vehicle. Thus the vehicle is easily maneuverable, pro
Since variations of the present combination may be
duces little drag, and is adapted to be propelled in any
made within the concept of the invention, I wish to re
desired direction. The substantially plane bottom of the
serve to myself all modifications thereof that may fall
vehicle functions in ilight yas do the wings of a wing type
within the scope of the pending claims.
I claim:
A vertical stabilizing fin 9 of substantial height is
l. In a wingless gas jet discharge engine-propelled
affixed to the top body wall of the vehicle, at the rear
heavier than air flying vehicle which is devoid of con
thereof, substantially as shown. The location of the tail
fin 9 above the forward-propelling yand steering engine 6 70 nection to subjacent ground or water when in flight, so
as to be adapted for high speed llying at from low to
and just rearwardly of the plane of the left engines 6a
high altitudes, said vehicle having walls providing a hol
is important in that it cooperates with the former to
low fuselage which is substantially oval in top plan, said
fuselage providing a substantially plane bottom Wall and
posed in said fuselage space and in a position substan->
merging side and top walls which are convexly curved
both transversely and longitudinally throughout their eX
tent and the length of the fuselage, said fuselage hav
ing an interior and forwardly closed engine-receiving
space at least in part provided by said top, bottom, and
side fuselage walls; two first and one second gas dis
mounting said engine in a downwardly discharging and
substantially vertical position entirely within said fuse
tially forward of the rear end of said fuselage, means f
lage space to vertically lift or controllably lower the ve
hicle for a landing; said vehicle fuselage having a sub
stantially plane bottom wall constituting the bottom wall
Y of said space and provided with an opening therethrough,
vsaid first reaction engine being disposed to direct its re
charge type reaction engines disposed entirely within said
fuselage space, the two first engines in said space being l0 action force downwardly through said opening to pro
duce a vertical draft therethrough to produce said ver
located approximately midway the length of said fuse
tical lift, or a controlled slow descent; at least one sec
lage and adjacent opposite sides of the latter; the bottom
ond gas discharge type reaction engine for vehicle Vsteer
wall of said engine-receiving space constituting the bot
ingand forward propulsion purposes and also disposed
tom wall of said fuselage and provided with an opening
entirely within said interior fuselage space but in a posi
extending therethrough adjacent each side, mounting
tion adjacent the rear end of the vehicle fuselage, said
means for each of said lirst engines carried by said bot
rear fuselage end having an openingtherein, at least the
tom wall and surrounding the respective openings there
side, top and rear walls of the engine-providing space
in as a bottom fuselage wall reinforcement at the site of
of said fuselage being substantially imperforate except
said openings, said first engines being disposed in a down
wardly discharging and substantially vertical position
and directing their'reacting forces downwardly through
20 for said aforementioned rear fuselage opening when they Y
said bottom wall openings, whereby to vertically lift or
controlledly lower the vehicle for a landing, the second
single gas discharge type reaction engine having a rear
of substantially greater widthwise area than the gas dis
wardly directed gas discharge end and constituting the
vehicle is in ñight, and said rear fuselage opening begingV
charge portion of said second engine; a circular fuselage
yWall area-reinforcing tracking afñxed to said fuselage
25 Within and adjacent the rear of said space, a member-on »
steering and forward propulsion means for said vehicle,
said single second engine located adjacent the rear end Y
of both the vehicle fuselage and engine-receiving space,
said rear fuselage end having an opening therein com
which said second engine is affixed and which is revolu
bly engaged with said tracking to turn in a horizontal
plane around its axis through any 'desired angle, said
second engine being disposed with relation to said rear
municating directly with said engine-receiving space, at 30 fuselage opening to direct its reaction force therethrough
during all positions of operative adjustment thereof rela-I
least the top and side walls of said engine-providing
tive to said fixed trackway, an upstanding stabilizing -ñn
space being imperforate when the vehicle is in ñight, said
of substantial height as compared to fuselage depth and
rear fuselage opening being of substantially greater width
ñxedly carried by the upper exterior central top wall por
wise area than the gas discharge end of said second en
gine, a circular tracking within said space and añixed to 35 tion of said fuselage, said iin extending longitudinally
of the fuselage at a point above said second engine and `
one of the top and bottom -walls as a reinforcement for
same, a member on which Vsaid second engine Vis aíîixed
terminating adjacent the plane of said first engine, where
and which member is revolubly engaged with said track
by to cooperate with the latter as an aid in predeter»
minedly controlling turning of the vehicle in -flight, and Y
y ing to turn in a horizontal plane around its axis through
any desired angle, the discharge Vend of said second en 40 both said first and second engines cooperating to propel
said vehicle in flight with a minimum drag and a maxi
mum efficiency.
gine being disposed with relation to'said rear fuselage
opening to direct its reaction force therethrough during
all positions of operative Yadjustment thereof relative to
said fixed trackway, an upstanding stabilizing ñn fixedly ,
carried by the upper exterior portion of said fuselage ex
tending longitudinally of the latter above said second
engine to a point adjacent the plane of the lìrst two en
gines and being of substantial height as compared t0
fuselage depth, whereby to cooperate with the latter as
an aid in predeterminedly controlling turning of the ve 50
hicle in ñight, and said first and second engines coop
erating to propel said vehicle Vin flight with a minimum
drag and a maximum eñiciency.
2. yIn a wingless gas jet discharge engine propelled,
heavier than air ñying vehicle which is devoid of con 55
nection to'subjacent ground or water when in ñight, so
as to be adapted for high speed flying at from low to
high altitudes, said vehicle providing a fuselage having
an interior and forwardly closed'engine-receiving space,
at least one first gas discharge type reaction engine dis 60
References Cited in the file ofV this patent
Bajza _______________ __ Nov. 14, 19,11
Bauer _______________ __ Dec. 29, 1931
Snyder ______________ __ Apr. 26, 1932
Peck ________________ __ Jan. 3l, 1933 ~
Roth ________________ ___ Aug. 8, 1933
Wheeler ___________ ____ NOV._24, 1936
Madden ______________ __ Mar. 7,
Price ________________ __ Sept. 9,
Prieto ______________ __ May 11,
'Lippisch _____________ __ Feb. 14,
France ______________ __ Aug. 25, 1947
France ______________ __ Oct. 17, 1950
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